# Service difficulty reports: Dehavilland DHC-2

A list on [Dehavilland DHC-2](https://openairdocs.org/model/dehavilland-dhc-2.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 3 · 120 reports

- [SDR 21GA051820261487](https://openairdocs.org/sdr/21GA051820261487.md): Engine · faulted · May 15, 2026 · N1487 · Dhav DHC2* · Engine (Turbine/Turboprop)
  > DURING TAKEOFF ROLL, BETWEEN 60-70 KNOTS, WE HEARD TWO LOAD BANGS AND TOWER CANCELED OUR TAKEOFF CLEARANCE FROM SEEING SPARKS FROM ENGINE AND HEARING A LOUD BANG FROM THE TOWER. FROM THE COCKPIT THEY HAD NORMAL ENGINE INDICATIONS AND NO FIRE WARNING. WE CLEA
- [SDR 2020F00365](https://openairdocs.org/sdr/2020F00365.md): Tie Rod · corroded · Jul 22, 2019 · N4444Z · Dhav DHC2* · Wheel/Ski/Float
  > ALL 4 LOWER FLOAT TIE-ROD (FLYING WIRES) WIRE PULLS SHOW SIGNS OF CORROSION AND ATTACHMENT HOLE ELONGATION.
- [SDR CA190709009](https://openairdocs.org/sdr/CA190709009.md): Tab · cracked · Jun 17, 2019 · Dhav DHC2* · Elevator, Tab Structure
  > (CAN) DURING A 100 HOUR INSPECTION, MULTIPLE CRACKS WERE FOUND IN THE ELEVATOR TRIM TAB SKIN AT THE ATTACH POINT FOR THE TRIM TAB ACTUATING HORN. TRIM TAB WAS REPAIRED AND RETURNED TO SERVICE. (TC# 20190709009)
- [SDR CA190730025](https://openairdocs.org/sdr/CA190730025.md): Fitting · cracked · May 24, 2019 · Dhav DHC2* · Wing, Landing Gear Attach Fittings
  > (CAN) DURING A SCHEDULED INSPECTION, THE FORWARD UPPER LH FLOAT FITTING WAS FOUND U/S DUE TO CORROSION/CRACKING. FITTING P/N 58-S-1022 WAS REPLACED WITH NEW TO RECTIFY. ALL WORK PERFORMED IAW THE APPLICABLE MAINTENANCE PUBLICATIONS (TC# 20190730025)
- [SDR CA190509008](https://openairdocs.org/sdr/CA190509008.md): Fly Wire · chafed · May 8, 2019 · Dhav DHC2* · Wheel/Ski/Float
  > (CAN) DURING AMPHIBIOUS FLOAT REMOVAL LAST FALL NOTICED AFT FLY WIRES CHAFFED AT MID POINT. WIPAIRE 6100 IPC DOES NOT SPECIFY ANTI-CHAFE AND INTERSECTION OF FLY WIRES ON FLOATS. (TC# 20190509008)
- [SDR CA190417011](https://openairdocs.org/sdr/CA190417011.md): Turnbuckle · corroded · Apr 17, 2019 · Dhav DHC2* · Elevator Control System
  > (CAN) BOTH ELEVATOR CABLES FORK END ARE IN A VERY CORROSIVE LOCATION FOR MARINE FLOAT PLANES. ONE FORK END SNAPPED JUST BY UNSCREWING IT FROM THE TURNBUCKLE BY HAND DURING AN INSPECTION. I WOULD SUGGEST TO REPLACE BY THE EQUIVALENT IN STAINLESS STEEL P/N: MS21
- [SDR CA180423020](https://openairdocs.org/sdr/CA180423020.md): Channel · cracked · Apr 19, 2018 · Dhav DHC2* · Horizontal Stabilizer Structure
  > (CAN) DURING A SCHEDULED INSPECTION, THE HORIZONTAL CHANNEL PN C2FS535-5 ATTACHED THE 228 BULKHEAD WAS FOUND CRACKED AT THE RUDDER STOP ATTACHMENT BOLT HOLES. THE CHANNEL WAS REPLACED TO RECTIFY THE DEFECT. PART TOTAL TIME WAS 25, 344.9 HRS. ALL WORK WAS PE
- [SDR CA180207024](https://openairdocs.org/sdr/CA180207024.md): Bearing · failed · Oct 6, 2017 · Dhav DHC2* · Reciprocating Engine Supercharger
  > (CAN) CONDITIONS FOUND ON DISMANTLING/INSPECTION: THE CAUSE OF THE ENGINE FAILURE WAS DUE TO IMPELLER BALL BEARING FAILURE. WHEN THE BALLS LEAVE THEIR RACES, THE IMPELLER ASSEMBLY (SHAFT AND IMPELLER) HAS ROOM TO MOVE FREELY. IT ENDS UP CONTACTING THE HOUSIN
- [SDR WM92012F00000](https://openairdocs.org/sdr/WM92012F00000.md): Fuel Tank · leaking · Aug 13, 2012 · N814DW · Dhav DHC2* · Fuel Storage
  > FRONT FUEL TANK DEVELOPED AN UNDETECTED LEAK VIA A SMALL CRACK IN THE LOWER CORNER NEAR A WELDED REPAIR. FUEL WAS IGNITED POSSIBLY VIA THE EXHAUST INTENSIFIER DURING ENGINE START-UP RESULTING IN A FIRE UNDER THE FLOOR IN THE FOWARD FUEL TANK BAY. RECOMMEND B
- [SDR 5ASR2011929003](https://openairdocs.org/sdr/5ASR2011929003.md): Adc · false indication · Sep 29, 2011 · N2513N · Dhav DHC2* · Air Data Computer
  > ALTITUDE OUT OF TOLERANCE. FAILED BIENNIAL INSPECTION.
- [SDR 2010FA0001250](https://openairdocs.org/sdr/2010FA0001250.md): Attach Bracket · corroded · Nov 9, 2010 · N233N · Dhav DHC2* · Horizontal Stabilizer, Attach Fittings
  > BOTH LT AND RT FWD HORIZ STABILIZER ATTACH BRACKETS WERE INSTALLED AS PART OF THE AOG AIR SUPPORT WING ANGLE MOD (STC SA01258NY) DURING ANNUAL INSP FOUND HORIZ STABILIZER FWD ATTACH TO BE LOOSE. PART IS ATTACHED TO THE FWD SPAR OF THE HORIZ STABILIZER WITH 2
- [SDR 2008FA0000042](https://openairdocs.org/sdr/2008FA0000042.md): Cylinder Head · cracked · Dec 12, 2007 · N777DH · Dhav DHC2* · Reciprocating Engine Cylinder Section
  > CYLINDER CRACKED IN THE AREA OF EXHAUST VALVE.
- [SDR T522007F00000](https://openairdocs.org/sdr/T522007F00000.md): Cylinder Head · cracked · Jun 26, 2007 · N695TK · Dhav DHC2* · Reciprocating Engine Cylinder Section
  > NR 2 CYLINDER WAS FOUND TO HAVE A CRACK ALL THE WAY AROUND THE HEAD JUST ABOVE THE SECOND COOLING FIN. (K)
- [SDR TQ0A20070005](https://openairdocs.org/sdr/TQ0A20070005.md): Supercharger · making metal · May 25, 2007 · N1018A · Dhav DHC2* · Reciprocating Engine Supercharger
  > ENGINE LOST SOME POWER ON DESCENT, ONCE THE PLANE LANDED, PILOT REPORTED A METAL TO METAL SOUND. ONCE MAINTENANCE ARRIVED A LARGE AMOUNT OF OIL WAS SEEN AT THE EXHAUST TAILPIPE. AFTER PULLING THE PROPELLER THROUGH, A HYDRAULIC LOCK OCCURED AND AT THAT POINT
- [SDR TQ0A20070004](https://openairdocs.org/sdr/TQ0A20070004.md): Cylinder · failed · May 11, 2007 · N930TG · Dhav DHC2* · Reciprocating Engine Cylinder Section
  > NR 4 CYLINDER FAILURE AND SEPARATION FROM ENGINE CASE. ROUGH ENGINE LANDING AT TAQUAN AIR.
- [SDR TQ0A0004](https://openairdocs.org/sdr/TQ0A0004.md): Bulkhead · cracked · Jun 2, 2006 · N5160G · Dhav DHC2* · Propeller Spinner Section
  > SPINNER BULKHEAD CRACKS AT REAR SECTION AND DELAMINATION OF EPOXY.
- [SDR 2005FA0001618](https://openairdocs.org/sdr/2005FA0001618.md): Distributor Gear · disintegrated · Dec 15, 2005 · N2740 · Dhav DHC2* · Magneto/Distributor
  > DURING CRUISE LT ENGINE BEGAN TO RUN ROUGH. MAINTENANCE TRACED PROBLEM TO LT MAG. UPON OPENING THE MAGNETO, DISCOVERED THE DISTRIBUTOR GEAR MISSING 98 PERCENT OF ITS TEETH WITH MANY BROKEN PIECES AND SHAVINGS INSIDE THE MAG. THE DISTRIBUTOR GEAR BUSHING IS
- [SDR TQ0A0003](https://openairdocs.org/sdr/TQ0A0003.md): Bulkhead · cracked · Dec 5, 2005 · N67667 · Dhav DHC2* · Propeller Spinner Section
  > SPINNER BULKHEAD CRACKED.
- [SDR TQ0A520050003](https://openairdocs.org/sdr/TQ0A520050003.md): Bulkhead · cracked · Nov 21, 2005 · N67667 · Dhav DHC2* · Propeller Spinner Section
  > SPINNER BULKHEAD CRACKED.
- [SDR TQ0A0512001](https://openairdocs.org/sdr/TQ0A0512001.md): Bulkhead · cracked · Nov 21, 2005 · N67667 · Dhav DHC2* · Propeller Spinner Section
  > SPINNER BULKHEAD CRACKED.
- [SDR CA051114002](https://openairdocs.org/sdr/CA051114002.md): Plate · cracked · Nov 1, 2005 · Dhav DHC2* · Propeller Spinner Section
  > (CAN) PART INSTALLED DEC 03, FOUND CRACKED AT REMOVAL FOR ENGINE CHANGE.
- [SDR CA051025001](https://openairdocs.org/sdr/CA051025001.md): Rod Bearing · broken · Oct 24, 2005 · Dhav DHC2* · Reciprocating Engine Power Section
  > (CAN) DURING INSPECTION PROGRAM OF PULLING A CYLINDER AND PERFORMING AN INTERNAL VISUAL (REPETITIVE 500 HRS), A MECHANIC NOTICED IMPACT MARKS ON THE PISTON SKIRT, ELSEWHERE INSIDE CASE. NOTICED A CHUNK OF METAL IN BOTTOM OF THE CASE APPROX 2INCHES BY.2500 INC
- [SDR CA051026008](https://openairdocs.org/sdr/CA051026008.md): Beta Ring · failed · Oct 11, 2005 · Dhav DHC2* · Propeller Controlling System
  > (CAN) IT WAS FOUND THAT THE CIRCLIP SECURING THE BETA BUSHING HAD PULLED AWAY FROM ITS SLOT. THIS WAS DUE TO IMPROPER ADJUSTMENT OF THE BETA RODS. IT IS RECOMMENDED TO FOLLOW THE INSTRUCTIONS FROM MFG PROPELLER MM P/N 118F PG.7-58 FIG. 7-27, REV.11 OCT 01.
- [SDR 2005FA0001500](https://openairdocs.org/sdr/2005FA0001500.md): Mount · cracked · Oct 1, 2005 · N37756 · Dhav DHC2* · Air Data Computer
  > DURING ANNUAL INSPECTION FOUND THE ADC TRAY CRACKED COMPLETELY ACROSS ONE END. (K)
- [SDR CA050916005](https://openairdocs.org/sdr/CA050916005.md): Engine · failed · Sep 13, 2005 · Dhav DHC2* · Reciprocating Engine Cylinder Section
  > (CAN) FIVE MINUTES INTO CRUISE FLIGHT AT 1000FT, THE CAPTAIN REPORTED A LOUD BANG, FOLLOWED BY A CONSTANT VIBRATION. TEMPS AND PRESSURES WERE CHECKED NORMAL. THE CAPTAIN ELECTED TO RETURN TO THE POINT OF DEPARTURE AND DECLARED AN EMERGENCY. FOLLOWING AN UNE
- [SDR CA050803003](https://openairdocs.org/sdr/CA050803003.md): Segment · cracked · Jul 28, 2005 · Dhav DHC2* · Engine Exhaust System
  > (CAN) THE PILOT REPORTED AN INTERMITTENT (POPPING) SOUND DURING ALL PHASES OF OPERATION. MAINTENANCE INVESTIGATION REVEALED A CRACK AND BLOWN EXHAUST GASKET ON NR 3 CYLINDER EXHAUST SEGMENT. THE CRACK EXTENDED AROUND MOST OF THE FLANGE, AND WAS CREEPING UP T
- [SDR CA050728005](https://openairdocs.org/sdr/CA050728005.md): Mechanism · broken · Jul 27, 2005 · Dhav DHC2* · Wheel/Ski/Float
  > (CAN) THE AIRCRAFT LANDED IN ROUGH WATER THE UPPER RT WIRE PULL P/N C2UF2291 FAILED.
- [SDR CA050728006](https://openairdocs.org/sdr/CA050728006.md): Fitting · cracked · Jul 22, 2005 · Dhav DHC2* · Wheel/Ski/Float
  > (CAN) INTERGRANULAR CORROSION AT FORWARD FLOAT STRUT FITTING P/N 585926R FOUND DURING A 400 HOUR INSPECTION.
- [SDR CA050728004](https://openairdocs.org/sdr/CA050728004.md): Cylinder Head · separated · Jul 20, 2005 · Dhav DHC2* · Reciprocating Engine Cylinder Section
  > DURING CRUISE FLIGHT, THE PILOT EXPERIENCED AN ENGINE VIBRATION.SUSPECTING A CYLINDER FAILURE, RETURNED TO BASE. TEMPS AND PRESSURES REMAINED NORMAL THROUGHOUT THE RETURN. MAINTENANCE INVESTIGATION REVEALED THAT THE NR 1 CYLINDER HEAD HAD SEPARATED FROM THE
- [SDR CA050728009](https://openairdocs.org/sdr/CA050728009.md): Lever · failed · Jul 17, 2005 · Dhav DHC2* · Power Lever
  > AIRCRAFT LANDED, WHILE FOLLOWING MARSHALLER'S HAND SIGNALS ONTO THE FBO RAMP, THE THROTTLE WAS ADVANCED TO COMPLETE TURN. WHEN THE THROTTLE WAS ADVANCED IT WAS UNRESPONSIVE ON TWO FULL MOVEMENTS. THE AIRCRAFT WAS SHUT DOWN WITH THE MIXTURE. A QUALIFIED AME
- [SDR CA050720003](https://openairdocs.org/sdr/CA050720003.md): Stud · cracked · Jul 4, 2005 · Dhav DHC2* · Reciprocating Engine Power Section
  > DURING AIRCRAFT 100HR INSPECTION, A SMALL CRACK WAS FOUND RUNNING FROM THRU BOLT TO A CYLINDER HOLD DOWN STUD ON REAR HALF OF POWER SECTION CASE BETWEEN NR 3 AND NR 4 CYLINDERS. ENGINE REMOVED FROM SERVICE FOR REPAIRS.
- [SDR CA050712008](https://openairdocs.org/sdr/CA050712008.md): Bellcrank · corroded · Jun 30, 2005 · Dhav DHC2* · Elevator Tab Control System
  > THE ELEVATOR CONTROL BELLCRANK LOCATED IN THE FUEL SELECTOR BAY WAS FOUND TO BE CORRODED AT THE INBOARD CABLE ATTACH POINT, SPECIFICALLY AT THE POINT WERE THE CABLE LINK PN NR C2CF347ND ATTACHES TO THE BELLCRANK.
- [SDR CA050705003](https://openairdocs.org/sdr/CA050705003.md): Crankcase · cracked · Jun 30, 2005 · Dhav DHC2* · Reciprocating Engine Power Section
  > (CAN) DURING A MAINTENANCE INSPECTION TO TROUBLESHOOT AIRCRAFT, OIL LEAK, MAINTENANCE DISCOVERED A CRACK IN THE CRANKCASE. AERO-ENGINES INC OUT OF LOS ANGLES REBUILT THIS ENGINE, BUT I WAS UNABLE TO FIND THEM FROM THE MANUFACTURER DROP-DOWN LIST. THE NUMBER
- [SDR CA050712007](https://openairdocs.org/sdr/CA050712007.md): Line · broken · Jun 13, 2005 · Dhav DHC2* · Aircraft Fuel Distribution System
  > DURING INSPECTION OF THE LT WING TIP FUEL TANK THE INTERNAL FUEL DELIVERY LINE WAS FOUND TO BE BROKEN AT THE INBOARD BULKHEAD ATTACH POINT (TACKWELD). THIS CONDITION IF RETURNED TO SERVICE WOULD NOT ALLOW THE FULL CONTENTS OF THE WING TANK TO BE TRANSFERED TO
- [SDR CA050623006](https://openairdocs.org/sdr/CA050623006.md): Attach Fitting · cracked · Jun 13, 2005 · Dhav DHC2* · Wheel/Ski/Float
  > UPON REMOVAL OF THE SPREADER BAR FROM THE FLOAT, A CRACK WAS NOTED ALONG THE CASTING SEAM OF THE RT FRONT FLOAT STRUT FITTING. THE ONLY TIME THIS AREA IS EXPOSED IS DURING HEAVY MAINTENANCE, WHERE THE AIRCRAFT IS REMOVED FROM FLOATS AND THE FLOATS ARE DISMANT
- [SDR CA050527016](https://openairdocs.org/sdr/CA050527016.md): Crankshaft · cracked · May 26, 2005 · Dhav DHC2* · Reciprocating Engine Power Section
  > THE ENGINE WAS RETURNED TO CANADA FROM THE USA FOLLOWING REPAIR AND INSTALLED ONDHC-2 MK 1 AIRCRAFT. WHEN THE ENGINE WAS STARTED EXCESSIVE OIL LEAK WAS OBSERVED FROM THE AREA NEAR THE REAR OF THE PROPELLER HUB AND THE NOSE CASE OF THE ENGINE. THE PROPELLER A
- [SDR CA050526004](https://openairdocs.org/sdr/CA050526004.md): Carburetor · failed · May 25, 2005 · Dhav DHC2* · Fuel Control/Reciprocating Engines
  > AFTER RETURNING FROM A FLIGHT, THE CREW REPORTED THAT THE ENGINE WOULD NOT IDLE BELOW 1000 RPM, AND WAS ROUGH AT INTERMEDIATE SPEEDS. IDLE MIXTURE ADJUSTMENT HAD NO EFFECT. THE CARBURETOR WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. UNIT WAS OVERH
- [SDR CA050712010](https://openairdocs.org/sdr/CA050712010.md): Bolt · cracked · May 18, 2005 · Dhav DHC2* · Engine Mount Section
  > (CAN) DURING A ROUTINE ENGINE MOUNT BOLT NDT INSPECTION, A CRACK WAS NOTED ON THE ENGINE SIDE OF THE ATTACH BOLT AT THE RADIUS WHERE THE TIE BAR PN NR MB100877 ATTACHES.
- [SDR CA050425011](https://openairdocs.org/sdr/CA050425011.md): Cylinder Head · cracked · Apr 25, 2005 · Dhav DHC2* · Reciprocating Engine Cylinder Section
  > (CAN) DURING ROUTINE INSPECTION, NR 9 CYLINDER HEAD WAS FOUND CRACKED. CRACK WAS LOCATED ON VERY TOP OF HEAD ON A LINE THAT WOULD CONNECT FRONT AND BACK SPARK PLUGS. CYLINDER WAS REPLACED AND AIRCRAFT INSPECTION COMPLETED AND AIRCRAFT RETURNED TO SERVICE.
- [SDR CA050421005](https://openairdocs.org/sdr/CA050421005.md): Nut · failed · Apr 18, 2005 · Dhav DHC2* · Propeller Assembly
  > (CAN) PROPELLOR DEPARTED FROM ENGINE. BOTH MECHANICS THAT INSTALLED PROPELLOR AND TORQUED NUT, CLAIMED 720 FT LBS CALCULATED WITH THEIR BODY WEIGHTS ON A LEVER ARM TO THE SPLINED WRENCH AND WITNESSED THE LOCK IN PLACE. MORE TO FOLLOW WHEN NUT HAS BEEN INDEPE
- [SDR 2005FA0000525](https://openairdocs.org/sdr/2005FA0000525.md): Adc · inoperative · Apr 6, 2005 · N60077 · Dhav DHC2* · Air Data Computer
  > AIR DATA COMPUTER (ADC) INSTALLED AS PART OF THE STC NR SA02207AK REPORTING VARING ALTITUDE ERROR UP TO 500 FT.
- [SDR 2005FA0000524](https://openairdocs.org/sdr/2005FA0000524.md): Adc · malfunctioned · Apr 6, 2005 · N47AK · Dhav DHC2* · Air Data Computer
  > THE ADC INSTALLED AS PART OF THE EFIS SYSTEM IAW STC NR SA02207AK WOULD NOT MAINTAIN A CONSTANT ACCURATE ALTITUDE READINGS. EACH TIME THE READING WAS RESET, THE ALTITUDE READING WOULD DEVIATE UP TO 2000 FT.
- [SDR CA050425010](https://openairdocs.org/sdr/CA050425010.md): Cylinder Head · separated · Apr 4, 2005 · Dhav DHC2* · Reciprocating Engine Cylinder Section
  > (CAN) HEAD SEPARATED FROM BARREL CAUSING SOME ENGINE POWER LOSS AND ROUGHNESS. PILOT LANDED PLANE ALONG ROUTE. CYLINDER ASSY WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.
- [SDR CA050401006](https://openairdocs.org/sdr/CA050401006.md): Washer · missing · Mar 23, 2005 · Dhav DHC2* · Wheel/Ski/Float
  > (CAN) WASHER WAS NOT INSTALLED ON AXLE UPON INSTALLATION OF SKIS. THIS CAUSED SKI TO SLIDE OFF AXLE ON LANDING, RESULTING IN AN OVERSHOOT. THE SKI DANGLED FROM THE CABLES AND BEAT AGAINST THE FUSELAGE CAUSING FURTHER DAMAGE BEFORE BREAKING FREE. THE PILOT THE
- [SDR CA050323009](https://openairdocs.org/sdr/CA050323009.md): Carburetor · failed · Mar 22, 2005 · Dhav DHC2* · Fuel Control/Reciprocating Engines
  > (CAN) THE FLIGHT CREW REPORTED THAT THE ENGINE WAS RUNNING ROUGH AT HIGH POWER SETTINGS AND RETURNED TO POINT OF ORIGIN. THE CARBURETOR WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. THERE WAS NO EVIDENCE OF FUEL CONTAMINATION IN THE FUEL TANKS, FUEL
- [SDR CA050311001](https://openairdocs.org/sdr/CA050311001.md): Cylinder Head · failed · Mar 9, 2005 · Dhav DHC2* · Reciprocating Engine Cylinder Section
  > (CAN) DURING CRUISE FLIGHT AT 1200 ASL, THE PILOT REPORTED A MISS IN THE ENGINE ACCOMPANIED WITH A REDUCTION IN CRUISE SPEED. CARB HEAT WAS SELECTED AND ENGINE CHECKS COMPLETED. SHORTLY THEREAFTER, THE ENGINE BACKFIRED 3 TIMES BUT CONTINUEDTO RUN NORMALLY BUT
- [SDR CA050330002](https://openairdocs.org/sdr/CA050330002.md): Crankcase · cracked · Mar 8, 2005 · Dhav DHC2* · Reciprocating Engine Power Section
  > (CAN) ENGINE HAD OIL LEAK WHICH WAS DETERMINED TO BE COMING FROM CRACK ON THE FRONT CRANKCASE BETWEEN NR 3 AND 4 CYLINDER BASE AREA. THIS CRACK WAS ABOUT 3.5 INCHES LONG ORGINATING FROM CRANKCASE THROUGH BOLT UP TOWARDS THE CYLINDER BASES.
- [SDR CA050303011](https://openairdocs.org/sdr/CA050303011.md): Rod · failed · Mar 3, 2005 · Dhav DHC2* · Elevator Tab Control System
  > (CAN) DURING CLIMB, PILOT EXPERIENCED A SLIGHT THUMP THROUGH ELEVATOR CONTROL SYSTEM, AND A MINOR VIBRATION WHICH STOPPED WHEN LEVEL FLIGHT WAS ACHIEVED. THE FLIGHT WAS CONTINUED TO DESTINATION WHERE MAINTENANCE WAS AVAILABLE. THE PILOT NOTED THAT MORE ELEVA
- [SDR CA050228005](https://openairdocs.org/sdr/CA050228005.md): Strut · corroded · Feb 18, 2005 · Dhav DHC2* · Wheel/Ski/Float
  > (CAN) DURING ANNUAL INSPECTION AND FLOAT REMOVAL, THE FWD RT FLOAT STRUT WAS FOUND TO HAVE LEVEL 2-3 CORROSION ON THE INSIDE OF THE STRUT. DUE TO THE FACT THAT ALL OTHER STRUTS WERE IN EXCELLENT CONDITION LEADS US TO BELIEVE THAT THIS STRUT WAS INSTALLED WITH
- [SDR CA050223008](https://openairdocs.org/sdr/CA050223008.md): Oil Cooler · leaking · Feb 10, 2005 · Dhav DHC2* · Engine Oil Cooler
  > (CAN) PILOT NOTICED DECREASING OIL PRESSURE APPROX 8 MINUTES FROM DESTINATION. UNEVENTFUL LANDING WAS CARRIED OUT. OIL PRESSURE DID NOT DROP BELOW 60 PSI, BUT OIL LEVEL IN TANK WAS BELOW BOTTOM OF DIPSTICK. APPROXIMATELY 3 TO 3.5 GALLONS OF OIL LOST IN UNDER

Next page: https://openairdocs.org/model/dehavilland-dhc-2/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy
FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
WHERE aircraft_model_key = 'DHC2'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/dehavilland-dhc-2/reports

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